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Effect of pressure level on afterburner-wall temperatures

Description: Report presenting an investigation conducted on a full-scale afterburner and turbojet engine to determine the effect of pressure level on afterburner-wall temperature. For a given ratio of cooling airflow to afterburner gas flow, the afterburner-wall temperature increased as afterburner-outlet pressure was increased. The results indicated that heat transfer by luminous radiation was not significant any pressure level investigated.
Date: June 11, 1958
Creator: Shillito, Thomas B. & Smolak, George R.
Partner: UNT Libraries Government Documents Department

Aerodynamic heating of blunt nose shapes at Mach numbers up to 14

Description: From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on this problem."
Date: August 11, 1958
Creator: Stoney, W. E., Jr.
Partner: UNT Libraries Government Documents Department

Analysis of Rocket, Ramjet, Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2: Rocket Missile Performance

Description: Memorandum presenting an investigation of the theoretical performance of a two-stage ballistic rocket missile with a centerbody and two parallel boosters for JP4-oxygen and ammonia-fluorine propellants. The missile using the ammonia-fluorine propellant weighs about one-half as much as a missile using JP4-oxygen. Results regarding the optimum missile and effect of variation of design parameters are provided.
Date: October 11, 1954
Creator: Huff, Vearl N. & Kerrebrock, Jack
Partner: UNT Libraries Government Documents Department

Preliminary Analysis of a Nuclear Powered Supersonic Airplane Using Ramjet Engines

Description: Report discussing performance estimates for several airplanes using General Electric AC-210 ramjet nuclear-powered engines. Assumptions used for designing the engines, radiation shield, and airframe are described. Potential tradeoffs in regards to power and weight reduction are also discussed.
Date: April 11, 1958
Creator: Weber, Richard J. & Connolley, Donald J.
Partner: UNT Libraries Government Documents Department

Flight, Analog-Simulator, and Analytical Studies of an Automatically Controlled Interceptor Which Uses a Bank-Angle-Error Computer for Lateral Commands

Description: Report presenting the tracking performance of an automatically controlled interceptor in which the deflection channel incorporated a bank-angle-error computer that commanded rolling velocities of the interceptor proportional to the computed bank-angle errors. Results regarding gravity terms included in bank-angle-error computation and a comparison of modified system using bank-angle-error computer with the prototype system are provided.
Date: August 11, 1958
Creator: Cheatham, Donald C. & Brissenden, Roy F.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of a 1/6-Scale Model of the Bumblebee XPM Missile at High Subsonic Speeds

Description: Report presenting an investigation of a model of the Bumblebee XPM missile to determine the causes of booster-fin failures for a range of Mach numbers and Reynolds numbers. The cause of fin failure was determined to be the launching shoes that caused the missiles to trim at increasingly negative angles of attack. Additional testing with wing spoilers and alternate booster fins was also conducted.
Date: December 11, 1950
Creator: Nelson, Warren H.
Partner: UNT Libraries Government Documents Department

Stability of Ballistic Reentry Bodies

Description: Report discussing various features of the stability of ballistic reentry shapes, including considerations for ballistic-missile and manned-satellite reentry capsules. Attainment of satisfactory stability of reentry bodies with subsonic terminal velocities was not found to be too difficult, but undesirable features that may cause marginal stability characteristics may be introduced in an effort to minimize weight. Reentry bodies with supersonic terminal velocities have fewer stability issues.
Date: August 11, 1958
Creator: Bird, John D. & Reese, David E., Jr.
Partner: UNT Libraries Government Documents Department

Drag and Static Stability at Low Lift of Rocket-Powered Models of the Convair MX-1626 Airplane at Mach Numbers From 0.7 to 1.5

Description: Report presenting flight testing on models of the proposed Consolidated Vultee Aircraft Corporation MX-1626 airplane with nacelles and without nacelles. Results regarding drag level, design modifications, dampening, trimming, and the use of ventral boosters are provided.
Date: June 11, 1953
Creator: Hall, James R. & Hopko, Russell N.
Partner: UNT Libraries Government Documents Department

Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular-Piloted Baffle-Type Flameholder

Description: "A ram-jet engine with an experimental 48-inch-diameter combustor was investigated in a free-jet facility. The combustor design comprised a large-volume annular pilot region and an array of sloping baffle- or gutter-type flameholders. The combustor was intended to operate at a fuel-air ratio of about 0.037" (p. 1).
Date: May 11, 1955
Creator: Rayle, Warren D.; Smith, Ivan D. & Wentworth, Carl B.
Partner: UNT Libraries Government Documents Department

Effects of Secondary-Air Flow on Annular Base Force of a Supersonic Airplane

Description: Memorandum presenting an investigation of the effect of base bleed on the base force of a supersonic-interceptor model in the 8- by 6-foot supersonic wind tunnel. Generally, base pressures greater than ambient were obtained at the engine operating pressure ratios of the primary nozzle.
Date: October 11, 1954
Creator: Vargo, Donald J.
Partner: UNT Libraries Government Documents Department

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 1. - Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Lift and Drag; Mach Number, 1.61

Description: Memorandum presenting a supersonic wind-tunnel investigation of the origin and distribution of store interference in the 4- by 4-foot supersonic pressure tunnel at Mach number 1.6 in which separate forces on a store, a fuselage, a swept wing, and a swept-wing-fuselage combination were measured. The store was separately sting-mounted on its own six-component internal balance and was traversed through a wide systematic range of spanwise, chordwise, and vertical positions.
Date: March 11, 1955
Creator: Smith, Norman F. & Carlson, Harry W.
Partner: UNT Libraries Government Documents Department

Analysis of Meteorological Data Obtained During Flight in a Supercooled Stratiform Cloud of High Liquid-Water Content

Description: "Flight icing-rate data obtained in a dense and abnormally deep supercooled stratiform cloud system indicated the existence of liquid-water contents generally exceeding values in amount and extent previously reported over the midwestern sections of the United States. Additional information obtained during descent through a part of the cloud system indicated liquid-water contents that significantly exceeded theoretical values, especially near the middle of the cloud layer. The growth of cloud droplets to sizes that resulted in sedimentation from the upper portions of the cloud is considered to be a possible cause of the high water contents near the center of the cloud layer" (p. 1).
Date: July 11, 1951
Creator: Perkins, Porter J. & Kline, Dwight B.
Partner: UNT Libraries Government Documents Department

An Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XF3H-1 Airplane

Description: Report presenting an investigation of the low-speed, power-off stability and control characteristics of a model of the McDonnell XF3H-1 airplane. Flight testing occurred in the clean and slat- and flaps-extended conditions over a range of lift coefficients.
Date: October 11, 1951
Creator: Draper, John W.
Partner: UNT Libraries Government Documents Department

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

Description: "Results are presented of a free-flight investigation between Mach numbers of 0.7 to 1.3 and Reynolds numbers of 3.1 x 10(exp 6) to 7.0 x 10(exp 6) to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. This missile has a wing, body, and vertical tail, but has no horizontal tail. The basic wing plan form has an aspect ratio of 5.5, 45 deg of sweepback of the 0.406 streamwise chord line, and a taper ratio of 0.4" (p. 1).
Date: February 11, 1955
Creator: Arbic, Richard G.
Partner: UNT Libraries Government Documents Department

Effect of Dissociation on Exhaust-Nozzle Performance

Description: Memorandum presenting net jet thrusts for stoichiometric hydrocarbon-air, hydrogen-air and pentaborane-air mixtures for equilibrium and frozen expansion in the exhaust nozzle at flight Mach numbers up to 10. Net jet thrusts for equilibrium flow were three to five times that for frozen flow at Mach 10 for the three fuels cited, a hydrocarbon, hydrogen, and pentaborane. Results regarding dissociation energies, reaction rate, residence time, and estimated minimum performance are provided.
Date: June 11, 1958
Creator: Reynolds, T. W.
Partner: UNT Libraries Government Documents Department

Performance of JP-4 Fuel With Fluorine-Oxygen Mixtures in 1000-Pound-Thrust Rocket Engines

Description: Memorandum presenting seven injectors of four different types that were tested for use with JP-4-oxygen-fluorine propellant combinations. By using the best of the injectors, high characteristic velocities were obtained over the complete range of 0- to 70-percent fluorine in the oxidant. Results regarding injector performance, heat rejection, injector with triplet-jet elements in skewed array, and fluorine addition are provided.
Date: June 11, 1958
Creator: Nored, Donald L. & Douglass, Howard W.
Partner: UNT Libraries Government Documents Department

Flutter Tests of a 1/25-Scale Model of the B-36J/RF-84F Tip-Coupled Airplane Configuration in the Langley 19-Foot Pressure Tunnel

Description: Report discussing tests of a model of a B-36J/RF-84F tip-coupled airplane to evaluate the flutter characteristics where bomber-body freedoms are allowed and to obtain information about the dynamic stability characteristics. The variables studied were the skew angle of the fighter-bomber coupling, the fighter longitudinal position, the fighter and bomber loading, angle of sideslip, degrees of body freedom, and number of fighters. Flutter was primarily found to occur when the fighter roll frequency was near the natural chordwise-bending frequency of the bomber wing.
Date: January 11, 1956
Creator: Neely, Robert H.
Partner: UNT Libraries Government Documents Department

Investigation at Mach Number 1.91 of Spreading Characteristics of Jet Expanding From Choked Nozzles

Description: Report presenting an investigation at Mach number 1.91 to determine the gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles using total-temperature surveys. Results regarding the preliminary development and jet spreading characteristics of the different types of nozzles are provided.
Date: February 11, 1952
Creator: Rousso, Morris D. & Baughman, L. Eugene
Partner: UNT Libraries Government Documents Department

Preliminary flight investigation of the wing-dropping tendency and lateral-control characteristics of a 35 degree swept-wing airplane at transonic Mach numbers

Description: Report presenting results from a preliminary flight investigation on a swept-wing airplane of the lateral-control characteristics and wing-dropping tendency encountered at high Mach numbers. Measurements of aileron and rudder-control effectiveness are presented and used with estimated damping-in-roll characteristics and data from steady sideslips to approximate the variation of effective dihedral with Mach number.
Date: September 11, 1950
Creator: Rathert, George A., Jr.; Rolls, L. Stewart; Winograd, Lee & Cooper, George E.
Partner: UNT Libraries Government Documents Department

Preliminary flight investigation of the dynamic longitudinal-stability characteristics of a 35 degree swept-wing airplane

Description: Report presenting flight measurements of the dynamic longitudinal-stability characteristics of a 35 degree swept-wing airplane. The results indicated that a sharp reduction in damping at a Mach number of 0.92 with maximum damping occurred at Mach number of 0.88 and 0.94. Results regarding oscillation periods, damping coefficients, scatter, and number of cycles required for oscillations to damp to a certain amplitude are provided.
Date: December 11, 1950
Creator: Triplett, William C. & Van Dyke, Rudolph D., Jr.
Partner: UNT Libraries Government Documents Department

Flight measurements with the Douglas D-558-II (BuAero No. 37974) research airplane : determination of the aerodynamic center and zero-lift pitching-moment coefficient of the wing-fuselage combination by means of tail-load measurements in the Mach num

Description: Report presenting flight measurements of aerodynamic tail loads made on the Douglas D-558-II from which the variation with Mach number of the wing-fuselage aerodynamic center, static-longitudinal-stability parameter, the tail load per g, and the zero-lift wing-fuselage pitching-moment coefficient determined up to Mach number 0.87.
Date: July 11, 1950
Creator: Mayer, John P.; Valentine, George M. & Mayer, Geraldine C.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a flying-boat hull having a length-beam ratio of 15 and a warped forebody

Description: From Introduction: "The results of two phases of this investigation, presented in references 1 and 2, have indicated possible ways of reducing hull drag without causing large changes in aerodynamic stability and hydrodynamic performance."
Date: February 11, 1949
Creator: MacLeod, Richard G.
Partner: UNT Libraries Government Documents Department